CN115235293A - 一种透波防热一体化轻质复合结构陶瓷及其制备方法、应用 - Google Patents
一种透波防热一体化轻质复合结构陶瓷及其制备方法、应用 Download PDFInfo
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Abstract
本发明公开一种透波防热一体化轻质复合结构陶瓷及其制备方法、应用,该陶瓷面板和背板采用SiO2f/SiO2陶瓷基复合材料以提高陶瓷装甲整体的耐热性能,达到良好的热防护效果,主体则能实现冲击的能量吸收以达到防弹的效果。以氰酸酯树脂做粘接剂,耐高温,且具有良好的透波性能,可以很好满足军用直升机的防护需求和作战需要。此外,背板选用SiO2f/SiO2陶瓷基复合材料,整体轻质耐磨,在主体吸能破碎后,可以将破碎主体限制在陶瓷内部而不到处散落,起到良好的收集限制作用,SiO2f/SiO2陶瓷基复合材料突出轻质化的特点可显著降低军用直升机弹击核心防护区域的防弹装甲所占用的重量比例,使其在军用直升机防护上更具有优势。
Description
技术领域
本发明涉及陶瓷基复合材料技术领域,尤其是一种透波防热一体化轻质复合结构陶瓷及其制备方法、应用。
背景技术
武装直升机是现代化战争中不可缺少的武装打击力量,其强大的机动性能极大的提高了陆军作战能力,在现有立体化作战模式下发挥着不可替代的特殊作用,可完成保障运输、火力支援、搜索救援等多样化军事行动。但作战特性导致其容易被地面火力击中,在装甲防护能力不足的情况下容易造成坠毁。在目前国内直升机发动机性能的限制下,要解决这一问题,实现直升机装甲的合理配置,必须从趋势上向轻量化、复合化和多功能化方向发展。
发明内容
本发明提供一种透波防热一体化轻质复合结构陶瓷及其制备方法、应用,用于克服现有技术中装甲防护能力不足,不能兼顾轻量化和多功能化等缺陷。
为实现上述目的,本发明提出一种透波防热一体化轻质复合结构陶瓷,所述陶瓷为层状结构,依次包括面板、主体和背板;所述面板、主体和背板之间通过氰酸酯树脂粘接;
所述主体为氧化铝陶瓷整板;
所述面板和背板均为SiO2f/SiO2陶瓷基复合材料。
为实现上述目的,本发明还提出一种如上述所述透波防热一体化轻质复合结构陶瓷的制备方法,包括以下步骤:
(1)制备SiO2f/SiO2陶瓷基复合材料;
(2)按照SiO2f/SiO2陶瓷基复合材料、氧化铝陶瓷整板、SiO2f/SiO2陶瓷基复合材料的顺序进行粘接,粘接剂为氰酸酯树脂
为实现上述目的,本发明还提出一种透波防热一体化轻质复合结构陶瓷的应用,将上述所述陶瓷或者上述所述制备方法制备得到的陶瓷应用于军用直升机中。
与现有技术相比,本发明的有益效果有:
本发明提供的透波防热一体化轻质复合结构陶瓷装甲,面板和背板采用SiO2f/SiO2陶瓷基复合材料以提高陶瓷装甲整体的耐热性能,达到良好的热防护效果,主体则能实现冲击的能量吸收以达到防弹的效果。以氰酸酯树脂做粘接剂,耐高温,且具有良好的透波性能,可以很好满足军用直升机的防护需求和作战需要。此外,背板选用SiO2f/SiO2陶瓷基复合材料,整体轻质耐磨,在主体吸能破碎后,可以将破碎主体限制在装甲内部而不到处散落,起到良好的收集限制作用,SiO2f/SiO2陶瓷基复合材料对比高强度钢,拥有密度小、强度高、抗氧化和透波等的优点,突出轻质化的特点可显著降低军用直升机弹击核心防护区域的防弹装甲所占用的重量比例,使其在军用直升机防护上更具有优势。
附图说明
为了更清楚地说明本发明实施例或现有技术中的技术方案,下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍,显而易见地,下面描述中的附图仅仅是本发明的一些实施例,对于本领域普通技术人员来讲,在不付出创造性劳动的前提下,还可以根据这些附图示出的结构获得其他的附图。
图1为本发明提供的透波防热一体化轻质复合结构陶瓷的制备方法流程图;
图2为实施例1提供的透波防热一体化轻质复合结构陶瓷实物图。
本发明目的的实现、功能特点及优点将结合实施例,参照附图做进一步说明。
具体实施方式
下面将结合本发明实施例中的附图,对本发明实施例中的技术方案进行清楚、完整地描述,显然,所描述的实施例仅仅是本发明的一部分实施例,而不是全部的实施例。基于本发明中的实施例,本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例,都属于本发明保护的范围。
另外,本发明各个实施例之间的技术方案可以相互结合,但是必须是以本领域普通技术人员能够实现为基础,当技术方案的结合出现相互矛盾或无法实现时应当认为这种技术方案的结合不存在,也不在本发明要求的保护范围之内。
本发明提出一种透波防热一体化轻质复合结构陶瓷,所述陶瓷为层状结构,依次包括面板、主体和背板;所述面板、主体和背板之间通过氰酸酯树脂粘接;
所述主体为氧化铝陶瓷整板;
所述面板和背板均为SiO2f/SiO2陶瓷基复合材料。
优选地,所述主体的厚度为20~30mm;所述面板的厚度为2.0~5.0mm;所述背板的厚度为0.5~3.0mm。面板、主体和背板的厚度太厚,不利于粘接,且整体三层结构易被破坏;太薄,防隔热效果和防弹效果不佳。
优选地,所述主体的厚度为25mm;所述面板的厚度为2.0mm;所述背板的厚度为0.9mm。
优选地,所述主体的厚度为28mm;所述面板的厚度为3.5mm;所述背板的厚度为1.8mm。
优选地,所述主体的密度为≤2.4g/cm3,介电常数≤3.0,损耗角正切值≤8×10-3。
本发明还提出一种如上述所述透波防热一体化轻质复合结构陶瓷的制备方法,包括以下步骤:
(1)制备SiO2f/SiO2陶瓷基复合材料;
(2)按照SiO2f/SiO2陶瓷基复合材料、氧化铝陶瓷整板、SiO2f/SiO2陶瓷基复合材料的顺序进行粘接,粘接剂为氰酸酯树脂。
优选地,步骤(1)具体为:
S1:将SiO2织物真空浸渍于硅树脂溶液中,晾干;
S2:将步骤S1处理后的SiO2织物置于模具中夹紧,烧成,冷却至室温;
S3:重复S1~S2步骤若干次,至增重小于1%,得到SiO2f/SiO2陶瓷基复合材料。
优选地,在步骤S1中,所述硅树脂溶液浓度为30~60%。
优选地,在步骤S2中,所述烧成的温度为500~1000℃,时间为60~80min。
本发明还提出一种透波防热一体化轻质复合结构陶瓷的应用,将上述所述陶瓷或者上述所述制备方法制备得到的陶瓷应用于军用直升机中。
实施例1
本实施例提供一种透波防热一体化轻质复合结构陶瓷,该陶瓷为层状结构,依次包括面板、主体和背板;面板、主体和背板之间通过氰酸酯树脂粘接;
主体为氧化铝陶瓷整板;
面板和背板均为石英纤维织物增强的石英陶瓷基复合材料;
主体的厚度为25mm;面板的厚度为2.0mm;背板的厚度为0.9mm。
一体化轻质复合陶瓷的整体密度为2.2g/cm3。
本实施例还提供一种上述透波防热一体化轻质复合结构陶瓷的制备方法,如图1所示(上下表面即为面板、背板,芯层即为主体),包括以下步骤:
S1:将SiO2织物真空浸渍于硅树脂溶液中,浸渍4小时后取去晾干;硅树脂溶液浓度为50%;
S2:将步骤S1处理后的SiO2织物置于模具中夹紧,烧成温度为700℃,时间为60min,冷却至室温;烧成的温度为800℃,时间为70min
S3:重复S1~S2步骤8次,得到SiO2f/SiO2陶瓷基复合材料。
S4:按照SiO2f/SiO2陶瓷基复合材料、氧化铝陶瓷整板、SiO2f/SiO2陶瓷基复合材料的顺序进行粘接,粘接剂为氰酸酯树脂,粘结温度为150℃,固化时间为1小时,冷却后得到一体化轻质复合陶瓷,如图2所示。
复合陶瓷具有优异的耐高温透波防弹性能:
(1)一体化轻质复合陶瓷在800℃的高温环境下仍能保持51.6%的强度保留率。
(2)一体化轻质复合陶瓷放入120℃烘箱烘干4h,自然冷却后放入1000℃加热炉中持续10min,自然冷却到室温后继续放入1000℃加热炉中持续10min,重复10次,试样无裂痕、炸裂。
(3)一体化轻质复合陶瓷的介电常数2.9,损耗角正切值8×10-3(测试频率7.5GHz);
(4)一体化轻质复合陶瓷经1发56式7.62mm穿甲燃烧弹正面击发后未穿透,弹速超700m/s,背衬凹陷深度为21.7mm。
本实施例提供的透波防热一体化轻质复合结构陶瓷装甲可应用于军用直升机驾驶舱与油箱的整体防护中。
实施例2
本实施例提供一种透波防热一体化轻质复合结构陶瓷,该陶瓷为层状结构,依次包括面板、主体和背板;面板、主体和背板之间通过氰酸酯树脂粘接;
主体为氧化铝陶瓷整板;面板和背板均为石英纤维织物增强的石英陶瓷基复合材料;
主体的厚度为28mm;面板的厚度为3.5mm;背板的厚度为1.8mm。一体化轻质复合陶瓷的整体密度为2.4g/cm3。
本发明还提出一种透波防热一体化轻质复合结构陶瓷,包括以下步骤:
S1:将SiO2织物真空浸渍于硅树脂溶液(浓度60%)中,浸渍6小时后取去晾干;
S2:将步骤S1处理后的SiO2织物置于不锈钢模具中夹紧,烧成温度为700℃,时间为80min,冷却至室温;
S3:重复S1~S2步骤11次,得到SiO2f/SiO2陶瓷基复合材料。
S4:按照SiO2f/SiO2陶瓷基复合材料、氧化铝陶瓷、SiO2f/SiO2陶瓷基复合材料的顺序进行粘接,粘接剂为氰酸酯树脂溶液,粘结温度为150℃,固化时间为1小时,冷却后得到一体化轻质复合陶瓷。复合陶瓷具有优异的耐高温透波防弹性能:
(1)一体化轻质复合陶瓷在800℃的高温环境下仍能保持63.6%的强度保留率。
(2)一体化轻质复合陶瓷放入120℃烘箱烘干4h,自然冷却后放入1000℃加热炉中持续10min,自然冷却到室温后继续放入1000℃加热炉中持续10min,重复10次,试样无裂痕、炸裂。
(3)一体化轻质复合陶瓷的介电常数2.9,损耗角正切值7.8×10-3(测试频率7.5GHz);
(4)一体化轻质复合陶瓷经1发56式7.62mm穿甲燃烧弹正面击发后未穿透,弹速超700m/s,背衬凹陷深度为20.3mm。
本发明还提出一种透波防热一体化轻质复合结构陶瓷装甲的应用,应用于军用直升机驾驶舱与油箱的整体防护中。
以上所述仅为本发明的优选实施例,并非因此限制本发明的专利范围,凡是在本发明的发明构思下,利用本发明说明书及附图内容所作的等效结构变换,或直接/间接运用在其他相关的技术领域均包括在本发明的专利保护范围内。
Claims (10)
1.一种透波防热一体化轻质复合结构陶瓷,其特征在于,所述陶瓷为层状结构,依次包括面板、主体和背板;所述面板、主体和背板之间通过氰酸酯树脂粘接;
所述主体为氧化铝陶瓷整板;
所述面板和背板均为SiO2f/SiO2陶瓷基复合材料。
2.如权利要求1所述的透波防热一体化轻质复合结构陶瓷,其特征在于,所述主体的厚度为20~30mm;所述面板的厚度为2.0~5.0mm;所述背板的厚度为0.5~3.0mm。
3.如权利要求2所述的透波防热一体化轻质复合结构陶瓷,其特征在于,所述主体的厚度为25mm;所述面板的厚度为2.0mm;所述背板的厚度为0.9mm。
4.如权利要求2所述的透波防热一体化轻质复合结构陶瓷,其特征在于,所述主体的厚度为28mm;所述面板的厚度为3.5mm;所述背板的厚度为1.8mm。
5.如权利要求1所述的透波防热一体化轻质复合结构陶瓷,其特征在于,所述主体的密度为≤2.4g/cm3,介电常数≤3.0,损耗角正切值≤8×10-3。
6.一种如权利要求1~5任一项所述透波防热一体化轻质复合结构陶瓷的制备方法,其特征在于,包括以下步骤:
(1)制备SiO2f/SiO2陶瓷基复合材料;
(2)按照SiO2f/SiO2陶瓷基复合材料、氧化铝陶瓷整板、SiO2f/SiO2陶瓷基复合材料的顺序进行粘接,粘接剂为氰酸酯树脂。
7.如权利要求6所述的制备方法,其特征在于,步骤(1)具体为:
S1:将SiO2织物真空浸渍于硅树脂溶液中,晾干;
S2:将步骤S1处理后的SiO2织物置于模具中夹紧,烧成,冷却至室温;
S3:重复S1~S2步骤若干次,至增重小于1%,得到SiO2f/SiO2陶瓷基复合材料。
8.如权利要求6所述的制备方法,其特征在于,在步骤S1中,所述硅树脂溶液浓度为30~60%。
9.如权利要求6所述的制备方法,其特征在于,在步骤S2中,所述烧成的温度为500~1000℃,时间为60~80min。
10.一种透波防热一体化轻质复合结构陶瓷的应用,其特征在于,将权利要求1~5任一项所述陶瓷或者权利要求6~9任一项所述制备方法制备得到的陶瓷应用于军用直升机中。
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