CN113022033A - 防弹板和制作防弹板的方法 - Google Patents
防弹板和制作防弹板的方法 Download PDFInfo
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- CN113022033A CN113022033A CN202011425980.1A CN202011425980A CN113022033A CN 113022033 A CN113022033 A CN 113022033A CN 202011425980 A CN202011425980 A CN 202011425980A CN 113022033 A CN113022033 A CN 113022033A
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Abstract
本公开涉及防弹板和制作防弹板的方法。描述了一种防弹板,该防弹板包括具有第一主表面和第二主表面的芯层,所述芯层包括防弹凝胶。第一层的防弹材料在所述芯层的所述第一主表面上。第二层的防弹材料在所述芯层的所述第二主表面上。
Description
技术领域
本公开涉及防弹板和制作防弹板的方法。
背景技术
防弹板常常被用在期望进行防弹的应用中。常规的防弹板包括如图1中所示的采用非对称板构造的Kevlar纤维的多层层合物。在该多层层合物中采用了约1英寸厚的单个纸蜂窝芯10。该纸包括被压在一起的一组间位芳纶纤维。在间位芳香族聚酰胺纸的每个片材上铺设一系列水平行的环氧粘合剂。然后,将片材彼此上下堆叠并进行固化。然后,扩大每条粘结线之间的间隙,以创建六边形形状的蜂窝。通常,这些蜂窝是中空的(例如,填充有空气)。将其中浸渍有固化的环氧树脂的28层Kevlar层合物20利用粘合剂层30粘附到蜂窝芯10的一侧。铝面片材40利用附加的粘合剂层30粘附到蜂窝芯10和Kevlar层合物20。已知图1的防弹板用于例如飞机的机舱门,以保护飞行员免受恐怖威胁。
在实施方式中,图1的当前板满足防弹和刚度要求。然而,因为已知的防弹板是不对称的,所以它们在热固化期间遭受卷曲。为了减少卷曲,可使用冷粘结方法来制造图1的防弹板。然而,与在较高温度下执行的热粘结制造方法相比,这种冷粘结方法可增加制造板的时间并增加废品率。
因此,在本领域中需要可提供在采用热粘结方法的同时在卷曲减少废品较少的情况下制造的防弹板的材料和过程。
发明内容
本公开涉及一种防弹板。所述防弹板包括具有第一主表面和第二主表面的芯层,所述芯层包含防弹凝胶。第一层的防弹材料在所述芯层的所述第一主表面上。第二层的防弹材料在所述芯层的所述第二主表面上。
本公开还涉及一种制作防弹板的方法。所述方法包括提供具有第一主表面和第二主表面的芯层,所述芯层包含防弹凝胶。第一层的防弹材料附接在芯层的第一主表面上。第二层的防弹材料附接在芯层的第二主表面上。
应理解,以上总体描述和以下详细描述二者仅仅是示例性和说明性的,不是对要求保护的本教导的限制。
附图说明
并入且构成本说明书的一部分的附图例示了本教导的各方面,并且与描述一起用于说明本教导的原理。
图1例示了常规防弹板的示意性剖视图,该防弹板以非对称板构造采用Kevlar织物的多层层合物。
图2例示了根据本公开的防弹板的示意性剖视图。
图3例示了根据本公开的形成多个中空蜂窝的蜂窝壁和在装入蜂窝中以形成蜂窝芯层之前的防弹凝胶层的立体图。
图4例示了根据本公开的防弹板的示意性剖视图。
图5例示了根据本公开的防弹板的示意性剖视图。
图6例示了根据本公开的防弹板的示意性剖视图。
图7例示了根据本公开的可作为芯层被包括在图6的防弹板中的层合物结构的示意性剖视图。
图8例示了根据本公开的飞机的防弹门。
图9例示了根据本公开的制作防弹板的方法的流程图。
应该注意,附图的一些细节已被简化并且被绘制成促进理解,而不是维持严格的结构准确性、细节和比例。
具体实施方式
现在,将详细参照本教导,在附图中例示了本教导的示例。在附图中,类似的附图标记始终用于指定相同的元件。在以下的描述中,参考形成该描述的一部分的附图,并且在附图中通过图示的方式示出了实践本教导的具体示例。因此,以下描述仅仅是示例性的。
由于板部件的热膨胀系数(CTE)的差异,如图1中所示的防弹板在使用热粘结方法进行制造期间表现出卷曲。这会导致浪费时间和费用来修复卷曲的板,或者有可能会导致板完全报废。另外,板的卷曲经常导致板部件的某种形式的脱粘。一旦发生脱粘,板就将失去大量原本为其所设计的关键机械性能,诸如,例如抗弯强度显著降低。由于受热并随后冷却的板部件被非对称堆叠,导致会发生复合板的卷曲。在这种情况下,非对称部分是由于大的多层KEVLAR防弹层合物20导致的,该大的多层KEVLAR防弹层合物20用于满足板的防弹要求并且仅被堆叠在蜂窝芯的一侧。遗憾的是,将多层Kevlar织物重新分布成绕蜂窝芯10对称分布的两个较小的、分开的层合物若不被进一步改造将不能满足防弹要求。此外,为构造对称地添加另一层合物(例如,防弹层合物20的复制品)可减少卷曲,但将大大增加重量,从而增加了采用该板的飞机的燃料消耗。这进而给航空公司客户增加了大量的成本。
本公开的防弹板的对称设计在仍允许通过热粘结方法进行制造的同时将卷曲减小到可接受的水平内。热粘结采用诸如(例如)高于200°F(诸如(例如)约220°F至约500°F)这样的相对高的温度,从而可提高生产率。在示例中,热粘结可在约80PSI下在约275°F至约300°F的温度下进行25至30分钟。包括例如填充有防弹凝胶的蜂窝的芯层或如本文中所述的其他芯层材料被粘附在防弹材料的两个分开的多层层合物之间,以提供实现所期望防弹保护的单个内聚层合物结构。在实施方式中,包括填充有防弹凝胶的蜂窝的芯层具有比例如Kevlar层合物低的密度,由此提供了相对轻质的防弹材料。
图2例示了根据本公开的防弹板100的示例。防弹板包括具有第一主表面104和第二主表面106的芯层102。芯层102包括被构造为提供多个蜂窝110的蜂窝壁108。防弹凝胶112被内置于多个蜂窝110内,以形成蜂窝芯层。第一层的防弹材料120设置在芯层102的第一主表面104上。第二层的防弹材料122设置在芯层102的第二主表面106上。防弹凝胶充当桥接两个相对薄层的防弹材料120、122之间的间隙的第二防弹材料。
图3例示了在防弹凝胶112已被引入蜂窝110中之前的蜂窝壁108的立体图。蜂窝110可具有诸如具有六边形横截面的蜂窝形状这样的任何合适形状,如图3中例示的。其他示例包括具有正方形、矩形或其他多边形横截面的蜂窝。蜂窝壁108可包括适于以防弹结构容纳防弹凝胶112的任何材料。合适材料的示例是包括被压在一起的一组间位芳纶纤维的纸。可通过在多个间位芳族聚酰胺纸的片材上以一系列水平行施用环氧粘合剂来制造蜂窝壁108。将片材彼此上下堆叠并固化粘合剂。然后,扩大每条粘结线之间的间隙,以创建六边形形状的蜂窝。适用于制作蜂窝壁108的包括间位芳纶纤维的商购织物的示例是得自密歇根州米德兰的杜邦公司(DuPont)的在NOMEX中,芳族基团均在1和3位连接到主链,如下面的式1中所示的,其中,“n”是重复蜂窝的数量。这被称为间链接(meta-linkage)。
防弹凝胶112可以是任何膨胀的非牛顿流体,其具有在受到子弹撞击时表现出刚度增加的性质。这种防弹凝胶的示例是从英国伦敦的D3O Labs商购的D3OTM凝胶。D3O是包含聚氨酯和聚硼二甲基硅氧烷的能量吸收凝胶材料。D3O可以是诸如闭孔聚氨酯泡沫复合物这样的泡沫形式,该闭孔聚氨酯泡沫复合物包含作为分散在泡沫基质中的膨胀物的聚硼二甲基硅氧烷(PBDMS)。
蜂窝壁108在没有D3O凝胶的情况下提供极小的防弹阻力或者不提供防弹阻力,但确实向复合板赋予了刚度。芯层102可具有提供所期望防弹阻力的任何厚度。作为示例,芯层的厚度范围可为约0.2英寸至约5英寸,诸如,约0.5英寸至约2英寸或约0.5英寸至约1英寸。
第一层的防弹材料120和第二层的防弹材料122可包含任何合适的防弹材料。合适材料的示例是编织成织物并浸渍有可固化树脂的诸如KEVLAR(聚对苯二甲酰对苯二甲酰胺)纤维这样的对位芳纶纤维(para-aramid fiber)。在KEVLAR纤维中,芳族基团均在1和4位连接到主链,如下面的21中所示的,其中,“n”是重复蜂窝的数量。这被称为对链接。
树脂浸渍的KEVLAR纤维织物的多个层可与树脂层合在一起并进行固化。例如,第一层的防弹材料120和第二层的防弹材料122中的每个中可包括约5至约20层(诸如,约10至约20层或约10至约15层)的树脂浸渍织物。该树脂可以是诸如环氧树脂这样的适用于这种预浸渍层合物的任何合适的可固化树脂。该树脂可以是低热释放树脂,包括诸如酚醛树脂、苯并恶嗪树脂和氰酸酯基树脂这样的热固性树脂。也可使用诸如聚醚醚酮(PEEK)、聚醚酮酮(PEKK)、聚苯砜(PPSU)、聚苯硫醚(PPS)和聚醚酰亚胺(PEI)树脂这样的热塑性树脂。
第一层的防弹材料120和第二层的防弹材料122的厚度范围可均为约0.1英寸至约0.5英寸(诸如,约0.2英寸至约0.4英寸)。
图2的防弹板还包括第一层的防弹材料120上的第一面片材130和第二层的防弹材料122上的第二面片材132。作为示例,第一面片材130和第二面片材132均包含诸如纯铝(例如,99重量%或更多的铝)或铝合金这样的铝。面片材与芯一起提供抗弯刚度。另外,包含铝的面片材具有可有助于阻止子弹或弹片的性质。
第一面片材130和第二面片材132可具有任何所期望的厚度。合适的厚度范围的示例为约0.005英寸至约0.04英寸(诸如,约0.01英寸至约0.03英寸)。
图4例示了与以上针对图2描述的防弹板100相似的防弹板100,不同的是,图4的防弹板100包括在第一面片材130上的膨胀层140和装饰层160。膨胀层140用于向防弹板100提供耐火性。膨胀层包含膨胀材料,该膨胀材料可以是例如在存在热的情况下产生泡沫的有机材料配方。膨胀材料活化以形成泡沫的示例温度为约250°F至约450°F。倘若起火,泡沫材料充当对抗热渗透的热屏障。D3O凝胶将很可能不具有与纳入了凝胶的芳族聚酰胺芯相同的可燃性性质,并且膨胀材料可有助于为板提供所期望水平的耐火性。商购的膨胀材料的示例是树脂,树脂是得自例如北卡罗来纳州罗利市的FlameOFF Coatings有限公司或南卡罗来纳州的Ed Gregor and associates的一种热塑性膨胀层。在另一实施方式中,织物可预先浸渍有诸如这样的膨胀聚合物。这将很好地结合到复合叠层中,其中,一层或更多层预浸渍的织物(预浸料)可设置在防弹层合物的外表面上。膨胀层140可具有任何合适的厚度。作为示例,膨胀层140的厚度范围为约0.001英寸至约0.1英寸(诸如,约0.002英寸至约0.01英寸)。
装饰层160可设置在防弹板100上。这样的装饰层可包括例如墙纸、油漆、徽标或被施用以增强板的可视外观的任何其他所期望的层。这样的装饰层160可选地可被施用于本文中描述的任何防弹板。
图5示出了与图2的防弹板类似的防弹板100,不同的是,防弹板100包括在第一层的防弹材料120和第一面片材130之间的第一阻燃层146以及在第二层的防弹材料122和第二面片材132之间的第二阻燃层146。阻燃层可包括一层或更多层(诸如,约1至约10层、或约1至约5层、或约1至约3层)的浸渍有阻燃剂的织物。该织物可以是诸如织造的对位芳纶纤维(例如,或其他织物)这样的防弹材料。可采用诸如本文中描述的任何膨胀材料这样的任何合适的阻燃材料。商购的膨胀材料的示例是树脂,树脂是得自例如北卡罗来纳州罗利市的FlameOFF Coatings有限公司的一种热塑性膨胀层。在替代示例中,阻燃层146可包含浸渍在玻璃纤维织物中的膨胀材料。在又一示例中,阻燃层146可包含没有织物或纤维的膨胀材料(例如,仅有膨胀材料的层)。
防弹板100的一层或更多层可使用粘合剂层附接在一起。例如,第一粘合剂层150可将第一层的防弹材料120粘附到芯层102,第二粘合剂层150可将第二层的防弹材料122粘附到芯层102。可使用其他粘合剂层150将面片材130、132粘附到防弹板100。可采用提供层之间的足够粘结的任何合适的粘合剂材料。示例包括聚氨酯粘合剂和环氧粘合剂。
想到了本公开的防弹板的其他实现方式。作为示例,代替以上针对图2、图4和图5的芯层102讨论的蜂窝芯层,芯层可以是包含防弹凝胶的其他类型的层,诸如在没有被构造成提供多个蜂窝110的蜂窝壁108的情况下制成的防弹凝胶层。例如,芯层可以是仅有防弹凝胶泡沫的层。诸如本文中描述的D3OTM材料这样的合适的防弹凝胶泡沫材料的示例是本领域中已知的。在图6中例示了这种实现方式的示例,图6示出了包括芯层102的防弹板的示意性剖视图,芯层102包含没有蜂窝壁108的防弹凝胶泡沫。
在又一实现方式中,图6的防弹板的芯层102是包括多层防弹材料和一层或更多层防弹凝胶的层合结构。在图7中示出了这种层合结构的示例,该层合结构包括防弹材料的片材170以及设置在防弹材料170的片材之间并通过任何合适的手段(诸如,通过使用粘合剂(未示出))粘结到其的一层或更多层的防弹凝胶172。防弹材料可以是例如编织到织物中的诸如KEVLAR(聚对亚苯基对苯二甲酰胺)纤维这样的对位芳纶纤维。在图7的芯层102中,对位芳纶纤维织物可浸渍有或可不浸渍有可固化树脂。防弹凝胶可以是诸如(例如)本文中描述的D3O材料的层这样的防弹凝胶泡沫。图7的层合结构可被包括作为图6的防弹板100中的芯层102。
图6的防弹板100还包括防弹材料120、122的层;面片材130、132以及将这些层粘结在一起的粘合剂层150。防弹材料120、122的层、面片材130、132以及粘合剂层150可与以上相对于图2描述的那些相同。另外,防弹板100包括蜂窝层180和182。蜂窝层180、182包括形成蜂窝110并与以上相对于图3描述的蜂窝壁相同的蜂窝壁108,不同的是,蜂窝110填充有诸如空气这样的气体而非防弹凝胶。蜂窝层180、182使用合适的粘合剂150粘结到相邻的层。
在期望防弹保护的任何所期望应用中可采用本公开的防弹板。这种应用的示例包括飞机、航空器和其他用于军事目的的载具或结构的防弹。其他示例包括在商用飞机的客舱和机舱之间采用的防弹门板作为反恐措施以及期望相对质量轻的防弹保护的其他应用。
图8中示出了飞机202的防弹门200的示例。飞机202包括限定机身的外蒙皮205。飞机202的内部包括驾驶舱壁206,驾驶舱壁206包括防弹门200,防弹门200可以是例如驾驶舱门。驾驶舱壁206和防弹门200将驾驶舱区域或驾驶舱侧212与乘客区域或乘客侧214分开。防弹门200使得能够限制从乘客侧214进入驾驶舱侧212。如有需要,防弹门200也可用作机身内其他位置处的门。通常,防弹门200被形成为装配于驾驶舱壁206中的门框。防弹门200的一侧包括与门框的铰链208配合的铰链207。这使防弹门200能够被容易地打开和关闭。另外,防弹门200包括门闩或锁定机构209。锁定机构209与门框上的框锁定机构(未示出)配合,以将防弹门200锁定在关闭位置。
参照图9,本公开还涉及一种制作防弹板的方法。该方法包括提供具有第一主表面和第二主表面的芯层。芯层包括防弹凝胶。第一层的防弹材料附接在芯层的第一主表面上。第二层的防弹材料附接在芯层的第二主表面上。芯层、第一层的防弹材料和第二层的防弹材料可以是以上在本文中描述的任何那些层。
可选地,该方法可包括将附加层附接到防弹板。例如,可选地,该方法可包括将第一面片材附接在第一层的防弹材料上并且将第二面片材附接在第二层的防弹材料上。作为另一示例,可选地,该方法还可包括附接一层或更多层的被编织成织物并浸渍有阻燃剂的对位芳纶纤维。作为又一示例,可选地,该方法还可包括在第一面片材和/或第二面片材上施用可充当阻燃剂的膨胀层。作为另一示例,可选地,该方法可包括在附接第一面片材之前将第一蜂窝层附接到第一层的防弹材料以及在附接第二面片材之前将第二蜂窝层附接到第二层的防弹材料,第一蜂窝层和第二蜂窝层二者都包括形成多个蜂窝的蜂窝壁,该多个蜂窝填充有空气。与图6中例示类似地,第一面片材可附接到第一蜂窝层并且第二面片材可附接到第二蜂窝层。可在本公开的方法中采用本文中描述的面片材的层、被编织成织物并浸渍有第一阻燃剂的对位芳纶纤维的层、膨胀层、装饰层或蜂窝层中的任一者。
如图3中所示,芯层102可以是通过将防弹凝胶112装入由蜂窝壁108形成的多个蜂窝110中而制造的蜂窝芯层。例如,防弹凝胶112在缓慢施加的压力下充当液体,并且可被内置于蜂窝芯蜂窝中。可通过重力或其他合适的技术施加内置防弹凝胶112的压力。
如上所述,防弹板100的一层或更多层可使用粘合剂层粘附在一起。例如,该方法可包括使用粘合剂层150将第一层的防弹材料120粘附到芯层102以及将第二层的防弹材料122粘附到芯层102。可使用其他粘合剂层150将面片材130、132粘附到防弹板100。可通过热粘结方法执行粘附过程,该热粘结方法采用加热(诸如,在本文中描述的任何热粘结温度下)固化粘附层150。尽管因为与冷加工技术相比热粘结方法节省了加工时间所以热粘结方法是优选的,但如有需要,也可采用冷粘结方法。热粘结技术和冷粘结技术通常是本领域中众所周知的。
可通过任何合适的层技术将膨胀层140施用于面片材130、132。合适的层技术在本领域中是众所周知的,并且可由本领域的普通技术人员进行选择。在施用膨胀层140之前,可将底层涂料(未示出)施用到面片材。底层涂料有助于提供在膨胀层140和面片材之间的令人满意的粘附。
尽管阐述本公开的广泛范围的数值范围和参数是近似值,但在具体示例中阐述的数值被尽可能精确地报告。然而,任何数值都固有地包含某些误差,这些误差必定是由它们相应的测试测量中发现的标准偏差引起的。此外,将理解本文中公开的所有范围涵盖其中包含的任何和所有子范围。
另外,本公开包括根据以下条款的示例:
1.一种防弹板(100),该防弹板(100)包括:
具有第一主表面(104)和第二主表面(106)的芯层(102),所述芯层(102)包括防弹凝胶(112);
在所述芯层(102)的所述第一主表面(104)上的第一层的防弹材料(120);以及
在所述芯层(102)的所述第二主表面(106)上的第二层的防弹材料(122)。
2.根据条款1所述的防弹板(100),其中,所述芯层(102)是包括被构造成提供多个蜂窝(110)的蜂窝壁(108)的蜂窝芯层,所述防弹凝胶(112)被内置于所述多个蜂窝(110)内。
3.根据条款1或2所述的防弹板(100),其中,所述蜂窝壁(108)包含对位芳纶纤维。
4.根据条款1至3中任一项所述的防弹板(100),其中,所述防弹凝胶(112)是具有在受到子弹撞击时表现出刚度增加的性质的非牛顿流体。
5.根据条款1至4中任一项所述的防弹板(100),其中,所述芯层(102)的厚度范围为约0.2英寸至约5英寸。
6.根据条款1至5中任一项所述的防弹板(100),其中,所述第一层的防弹材料(120)和所述第二层的防弹材料(122)二者都包含浸渍有可固化树脂的对位芳纶纤维。
7.根据条款1至6中任一项所述的防弹板(100),其中,所述第一层的防弹材料(120)和所述第二层的防弹材料(122)的厚度范围均为约0.1英寸至约0.5英寸。
8.根据条款1至7中任一项所述的防弹板(100),所述防弹板(100)还包括第一粘合剂层(30)和第二粘合剂层(30),所述第一粘合剂层(30)将所述第一层的防弹材料(120)粘附到所述芯层(102)的所述第一主表面(104)并且所述第二粘合剂层(30)将所述第二层的防弹材料(122)粘附到所述芯层(102)的所述第二主表面(106)。
9.根据条款1至8中任一项所述的防弹板(100),所述防弹板(100)还包括所述第一层的防弹材料(120)上的第一面片材(130)和所述第二层的防弹材料(122)上的第二面片材(132)。
10.根据条款9所述的防弹板(100),其中,所述第一面片材(130)和所述第二面片材(132)均包含铝。
11.根据条款9所述的防弹板(100),其中,所述第一面片材(130)和所述第二面片材(132)的厚度范围均为约0.005英寸至约0.04英寸。
12.根据条款9所述的防弹板(100),所述防弹板(100)还包括在所述第一面片材(130)上的膨胀层(140)。
13.根据条款12所述的防弹板(100),其中,所述膨胀层(140)的厚度范围为约0.001英寸至约0.1英寸。
14.根据条款1至13中任一项所述的防弹板(100),所述防弹板(100)还包括选自以下的阻燃层(146):
i)一层或更多层的包括浸渍有阻燃剂的对位芳纶纤维的织物;
ii)包括浸渍有膨胀材料的玻璃纤维织物的层;以及
iii)仅有膨胀材料的层。
15.根据条款1至14中任一项所述的防弹板(100),所述防弹板(100)还包括在所述第一层的防弹材料(120)上的装饰层(160)。
16.根据条款1至15中任一项所述的防弹板(100),所述防弹板(100)还包括粘附到所述第一层的防弹材料(120)的第一蜂窝层和粘附到所述第二层的防弹材料(122)的第二蜂窝层,所述第一蜂窝层和所述第二蜂窝层二者都包括形成多个蜂窝(110)的蜂窝壁(108),所述多个蜂窝(110)填充有气体。
17.根据条款16所述的防弹板(100),其中,所述芯层(102)是包括多层的防弹材料(120)以及一层或更多层的防弹凝胶(112)的层合结构。
18.根据条款16所述的防弹板(100),其中,所述防弹凝胶(112)包括闭孔聚氨酯泡沫基质和分散在所述闭孔聚氨酯泡沫基质中的聚硼二甲基硅氧烷(PBDMS)。
19.一种飞机(202)的门,所述门包括条款1至18中任一项所述的防弹板(100)。
20.一种制作防弹板(100)的方法,该方法包括以下步骤:
提供具有第一主表面(104)和第二主表面(106)的芯层(102),所述芯层(102)包括防弹凝胶(112);
在所述芯层(102)的所述第一主表面(104)上附接第一层的防弹材料(120);并且
在所述芯层(102)的所述第二主表面(106)上附接第二层的防弹材料(122)。
21.根据条款20所述的方法,其中,所述芯层(102)是包括被构造成提供多个蜂窝(110)的蜂窝壁(108)的蜂窝芯层(102),所述防弹凝胶(112)被内置于所述多个蜂窝(110)内。
22.根据条款20或21所述的方法,其中,所述蜂窝壁(108)包含对位芳纶纤维。
23.根据条款20至22中任一项所述的方法,其中,所述防弹凝胶(112)是具有在受到子弹撞击时表现出刚度增加的性质的非牛顿流体。
24.根据条款20至23中任一项所述的方法,其中,所述第一层的防弹材料(120)和所述第二层的防弹材料(122)二者包含包括浸渍有可固化树脂的对位芳纶纤维的织物。
25.根据条款20至24中任一项所述的方法,所述方法还包括一层或更多层的织物,所述一层或更多层的织物包含浸渍有阻燃剂的对位芳纶纤维。
26.根据条款20至25中任一项所述的方法,其中,所述防弹板(100)是通过热粘结方法制成的。
27.根据条款20至26中任一项所述的方法,所述方法还包括在所述第一层的防弹材料(120)上附接第一面片材(130)并且在所述第二层的防弹材料(122)上附接第二面片材(132)。
28.根据条款27所述的方法,所述方法还包括在所述第一面片材(130)上施用膨胀层(140)。
29.根据条款27所述的方法,所述方法还包括在附接所述第一面片材(130)之前将第一蜂窝层附接到所述第一层的防弹材料(120)以及在附接所述第二面片材(132)之前将第二蜂窝层附接到所述第二层的防弹材料(122),所述第一蜂窝层和所述第二蜂窝层二者都包括形成多个蜂窝(110)的蜂窝壁(108),所述多个蜂窝(110)填充有气体。
尽管已针对一个或更多个实现方式例示了本教导,但是在不脱离所附权利要求书的精神和范围的情况下,可对所例示示例进行变更和/或修改。另外,虽然已经只相对于多种实现方式中的一个公开了本教导的特定特征,但这样的特征可与其他实现方式的一个或更多个其他特征组合,如任何给定或特定功能的期望和优势一样。此外,就在具体实施方式和权利要求中使用术语“包括”、“包含”、“具有”、“带有”或其变型的程度而言,这些术语旨在按与术语“包括”类似的方式被包括。另外,在本文中的讨论和权利要求书中,术语“约”指示所列出的值可略有改变,只要该改变没有导致处理或结构与本文中描述的预计目的不一致。最后,“示例性”指示该描述被用作示例,而不是意味着它是理想的。
应该理解,以上公开的和其他的特征和功能的变形形式或其替代形式可被组合成许多其他不同的系统或应用。本领域的技术人员随后可在其中进行各种目前未预见或无法预料的也旨在被随附权利要求书涵盖的替代形式、修改形式、变化形式或改进形式。
Claims (15)
1.一种防弹板(100),该防弹板(100)包括:
具有第一主表面(104)和第二主表面(106)的芯层(102),所述芯层(102)包括防弹凝胶(112);
在所述芯层(102)的所述第一主表面(104)上的第一层的防弹材料(120);以及
在所述芯层(102)的所述第二主表面(106)上的第二层的防弹材料(122)。
2.根据权利要求1所述的防弹板(100),其中,所述芯层(102)是包括被构造成提供多个蜂窝(110)的蜂窝壁(108)的蜂窝芯层,所述防弹凝胶(112)被内置于所述多个蜂窝(110)内。
3.根据权利要求1或2所述的防弹板(100),其中,所述蜂窝壁(108)包含对位芳纶纤维。
4.根据权利要求1或2所述的防弹板(100),其中,所述防弹凝胶(112)是具有在受到子弹撞击时表现出刚度增加的性质的非牛顿流体。
5.根据权利要求1或2所述的防弹板(100),其中,所述第一层的防弹材料(120)和所述第二层的防弹材料(122)二者都包含浸渍有可固化树脂的对位芳纶纤维。
6.根据权利要求1或2所述的防弹板(100),所述防弹板(100)还包括第一粘合剂层(30)和第二粘合剂层(30),所述第一粘合剂层(30)将所述第一层的防弹材料(120)粘附到所述芯层(102)的所述第一主表面(104)并且所述第二粘合剂层(30)将所述第二层的防弹材料(122)粘附到所述芯层(102)的所述第二主表面(106)。
7.根据权利要求1所述的防弹板(100),所述防弹板(100)还包括所述第一层的防弹材料(120)上的第一面片材(130)和所述第二层的防弹材料(122)上的第二面片材(132)。
8.根据权利要求7所述的防弹板(100),所述防弹板(100)还包括在所述第一面片材(130)上的膨胀层(140)。
9.根据权利要求1或2所述的防弹板(100),所述防弹板(100)还包括选自以下的阻燃层(146):
i)一层或更多层的包括浸渍有阻燃剂的对位芳纶纤维的织物;
ii)包括浸渍有膨胀材料的玻璃纤维织物的层;以及
iii)仅有膨胀材料的层。
10.根据权利要求1或2所述的防弹板(100),所述防弹板(100)还包括在所述第一层的防弹材料(120)上的装饰层(160)。
11.根据权利要求1所述的防弹板(100),所述防弹板(100)还包括粘附到所述第一层的防弹材料(120)的第一蜂窝层和粘附到所述第二层的防弹材料(122)的第二蜂窝层,所述第一蜂窝层和所述第二蜂窝层二者都包括形成多个蜂窝(110)的蜂窝壁(108),所述多个蜂窝(110)填充有气体。
12.根据权利要求11所述的防弹板(100),其中,所述芯层(102)是包括多层的防弹材料(120)以及一层或更多层的防弹凝胶(112)的层合结构,所述防弹凝胶(112)包括闭孔聚氨酯泡沫基质和分散在所述闭孔聚氨酯泡沫基质中的聚硼二甲基硅氧烷,即PBDMS。
13.一种飞机(202)的门,所述门包括权利要求1或2所述的防弹板(100)。
14.一种制作防弹板(100)的方法,该方法包括以下步骤:
提供具有第一主表面(104)和第二主表面(106)的芯层(102),所述芯层(102)包括防弹凝胶(112);
在所述芯层(102)的所述第一主表面(104)上附接第一层的防弹材料(120);并且
在所述芯层(102)的所述第二主表面(106)上附接第二层的防弹材料(122)。
15.根据权利要求14所述的方法,其中,所述防弹凝胶(112)是具有在受到子弹撞击时表现出刚度增加的性质的非牛顿流体。
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