CN106393915A - 防撞板及其制作方法 - Google Patents
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Abstract
本发明公开了一种防撞板及其制作方法,包括撞击层、缓冲层及吸能层;撞击层及吸能层之间为缓冲层,缓冲层包括2层或者3层纺纶蜂窝层,两层之间通过功能树脂粘结。纺纶蜂窝层的材质为纺纶蜂窝复合材料。每层纺纶蜂窝层的厚度均为5mm‑10mm。撞击层的材质为纺纶纤维,撞击层与缓冲层通过功能树脂粘结。吸能层的材质为高分子聚合物,吸能层与缓冲层通过功能树脂粘结。本发明采用全非金属防撞吸能结构板体,材质轻,吸能、防撞效果好,能有效保护机身内部结构,降低飞机后期维修费用。
Description
技术领域
本发明涉及飞行器防撞系统技术领域,尤其涉及一种防撞板及防撞板的制作方法。
背景技术
随着中国航空事业的发展,越来越多的飞行器以越来越快的速度飞行于蓝天,伴随而来的是因为鸟撞机而造成的重大飞行事故,该事故的发生越来越频繁。
防鸟撞板作为保证飞机高速飞行下的最后一道安全屏障,其防撞效果的好坏将直接影响飞机的安全。目前国内防鸟撞板技术还处于初级阶段,制版工艺及材料都为单一的铝板与金属蜂窝复合板材,材质较重,且防冲撞吸能效果不佳,而且往往在鸟撞后使得被保机身结构造成严重损伤,飞机后期维修费用高昂。
发明内容
为解决现有技术中,飞机上设置的防鸟撞的防撞板存在的防撞吸能效果差的技术问题,本发明的技术方案如下:
本发明中的防撞板,包括缓冲层;所述缓冲层为纺纶蜂窝结构板材。
在一种优选的实施方式中,所述缓冲层包括第一纺纶蜂窝层及第二纺纶蜂窝层,所述第一纺纶蜂窝层及所述第二纺纶蜂窝层的材料为纺纶蜂窝复合材料,所述第一纺纶蜂窝层及所述第二纺纶蜂窝层通过功能树脂粘结,使所述第一纺纶蜂窝层及所述第二纺纶蜂窝层构成纺纶蜂窝结构板材。所述第一纺纶蜂窝层的厚度及所述第二纺纶蜂窝层的厚度均为5mm-10mm。
在一种优选的实施方式中,所述缓冲层包括第一纺纶蜂窝层、第二纺纶蜂窝层及第三纺纶蜂窝层,所述第一纺纶蜂窝层、所述第二纺纶蜂窝层及所述第三纺纶蜂窝层的材料为纺纶蜂窝复合材料,所述第一纺纶蜂窝层、所述第二纺纶蜂窝层及所述第三纺纶蜂窝层通过功能树脂粘结,使所述第一纺纶蜂窝层、所述第二纺纶蜂窝层及所述第三纺纶蜂窝层构成纺纶蜂窝结构板材。所述第一纺纶蜂窝层的厚度、所述第二纺纶蜂窝层及所述第三纺纶蜂窝层的厚度均为5mm-10mm。
在一种优选的实施方式中,包括撞击层;所述撞击层的材质为纺纶纤维,所述撞击层与所述缓冲层通过功能树脂粘结。
在一种优选的实施方式中,包括吸能层;所述吸能层的材质为高分子聚合物,所述吸能层与所述缓冲层通过功能树脂粘结。
在一种优选的实施方式中,所述高分子聚合物为聚氨酯发泡材料。
在一种优选的实施方式中,所述功能树脂为双酚A型环氧树脂。
本发明中还包括防撞板的制作方法,具体步骤包括:
步骤1、根据飞机的型号及飞机机头防撞部位的大小,确定所需防撞板的尺寸;
步骤2、根据步骤1确定的防撞板的尺寸,制作防撞板的热模压模具;
步骤3、根据步骤1确定的防撞板的尺寸,制作相应尺寸的撞击层、缓冲层及吸能层;
步骤4、将步骤3的撞击层、缓冲层依次放入步骤1的模具中,并在撞击层与缓冲层之间涂覆双酚A型环氧树脂;
步骤5、将步骤4所得模具放入热模压设备中,加压使撞击层及缓冲层的间隙小于0.1mm-0.2mm,继而保压,保压时间为5min-15min;
步骤6、脱模,并在压合后的缓冲层的表面贴覆高分子聚合物。
本发明中的防撞板,与现有技术相比,其有益效果为:
本发明中的防撞板,包括多层不同厚度不同吸能效用的纺纶蜂窝复合材料、高强防弹纺纶纤维撞击层、高分子聚合物吸能层。利用高刚度和韧性的功能性树脂,将纺纶蜂窝、纺纶纤维撞击层以热模压方式压合成功能一体性,强阻拦结构体板材。阻拦板材压制成型后,背面贴覆高吸能、高缓冲的高分子聚合物,使得整个板体形成阻拦、缓冲、吸能的功能一体化结构,此结构在撞击实验中能有效的吸收冲击能量。结构中阻拦板体以防弹纤维层的撞击层形成防穿透高阻拦屏障,不同吸能蜂窝层随着撞击力及时间的变化吸收不同波段的冲击能量。高分子聚合物吸能层因撞击可瞬间硬化吸能的同时,并以热能的方式将冲击能量转换吸收,从而使整个结构板材具有优异抗冲击功能与能力。本发明采用全非金属防撞吸能结构板体,材质轻,吸能、防撞效果好,能有效保护机身内部结构,降低飞机后期维修费用。
附图说明
图1是本发明中防撞板的缓冲层为两层的结构示意图。
具体实施方式
下面将结合本发明的附图,对本发明的技术方案进行清楚、完整地描述。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。
实施例1
如图1所示,防撞板包括撞击层1、缓冲层及吸能层4,撞击层的材质为纺纶纤维。吸能层4的材质为高分子聚合物。缓冲层为纺纶蜂窝结构板材。撞击层1及吸能层4之间为缓冲层,缓冲层包括第一纺纶蜂窝层2及第二纺纶蜂窝层3。第一纺纶蜂窝层2的厚度为5mm,第二纺纶蜂窝层3的厚度为10mm。第一纺纶蜂窝层2的一个表面与撞击层1通过双酚A型环氧树脂连接,另一个表面与第二纺纶蜂窝层3一个表面通过双酚A型环氧树脂连接。第二纺纶蜂窝层3另一个表面通过双酚A型环氧树脂连接吸能层4,吸能层4采用的是聚氨酯发泡材料。使用时,将该防撞板的吸能层4与飞机机体连接,在飞鸟撞击机体时,飞鸟直接撞击在防撞板的撞击层1上,撞击层1接受的撞击力将会传输给缓冲层,由于撞击层1及缓冲层2均为纺纶纤维材质,纺纶纤维具有超高强度、重量轻、生命周期长等优良性能,加之缓冲层2为蜂窝结构,蜂窝结构强度高,两者组合在一起,可以使得飞鸟撞击时,由于纺纶纤维及蜂窝结构的强度均很高,飞鸟很难冲破撞击层1及缓冲层,不会发生飞鸟穿过防撞板直接撞击飞机内部零件的情况,保护了飞机内部的结构,避免了高昂的维修费用。另外,在缓冲层下还设有吸能层4,吸能层4将撞击的能量进行吸收,以免撞击力间接破坏飞机内部结构,达到有效保护机体的目的。本发明中的第一纺纶蜂窝层2的厚度为5mm-10mm,第二纺纶蜂窝层3的厚度为5mm-10mm。
实施例1防撞板的制作方法,包括:
步骤1、根据飞机的型号及飞机机头防撞部位的大小,确定所需防撞板的尺寸;
步骤2、根据步骤1确定的防撞板的尺寸,制作防撞板的热模压模具;
步骤3、根据步骤1确定的防撞板的尺寸,制作相应尺寸的撞击层、缓冲层及吸能层;
步骤4、将步骤3的撞击层、缓冲层依次放入步骤1的模具中,并在撞击层与缓冲层之间涂覆双酚A型环氧树脂;
步骤5、将步骤4所得模具放入热模压设备中,加压使撞击层及缓冲层的间隙小于0.13mm,继而保压,保压时间为5min;
步骤6、脱模,并在压合后的缓冲层的表面贴覆吸能层,吸能层为高分子聚合物。
高分子聚合物为聚氨酯发泡材料。
实施例2
本实施例在实施例1的基础上,将缓冲层改为三层结构,缓冲层包括第一纺纶蜂窝层、第二纺纶蜂窝层及第三纺纶蜂窝层,第一纺纶蜂窝层、第二纺纶蜂窝层及第三纺纶蜂窝层通过功能树脂粘结,第一纺纶蜂窝层、第二纺纶蜂窝层及第三纺纶蜂窝层的材料为纺纶蜂窝复合材料。第一纺纶蜂窝层的厚度为9mm,第二纺纶蜂窝层的厚度为10mm,第三纺纶蜂窝层的厚度为8mm。其他结构与实施例1相同。本实施例中的第一纺纶蜂窝层、第二纺纶蜂窝层及第三纺纶蜂窝层的厚度可以为5mm-10mm的组合。
实施例2防撞板的制作方法,包括:
步骤1、根据飞机的型号及飞机机头防撞部位的大小,确定所需防撞板的尺寸;
步骤2、根据步骤1确定的防撞板的尺寸,制作防撞板的热模压模具;
步骤3、根据步骤1确定的防撞板的尺寸,制作相应尺寸的撞击层、缓冲层及吸能层;
步骤4、将步骤3的撞击层、缓冲层依次放入步骤1的模具中,并在撞击层与缓冲层之间涂覆双酚A型环氧树脂;
步骤5、将步骤4所得模具放入热模压设备中,加压使撞击层及缓冲层的间隙小于0.15mm,继而保压,保压时间为15min;
步骤6、脱模,并在压合后的缓冲层的表面贴覆吸能层,吸能层为高分子聚合物。
以上所述,仅为本发明的具体实施方式,但本发明的保护范围并不局限于此,任何熟悉本技术领域的技术人员在本发明揭露的技术范围内,可轻易想到变化或替换,都应涵盖在本发明的保护范围之内。因此,本发明的保护范围应以所述权利要求的保护范围为准。
Claims (10)
1.防撞板,其特征在于,包括缓冲层;所述缓冲层为纺纶蜂窝结构板材。
2.根据权利要求1所述的防撞板,其特征在于,所述缓冲层包括第一纺纶蜂窝层及第二纺纶蜂窝层,所述第一纺纶蜂窝层及所述第二纺纶蜂窝层的材料为纺纶蜂窝复合材料,所述第一纺纶蜂窝层及所述第二纺纶蜂窝层通过功能树脂粘结,使所述第一纺纶蜂窝层及所述第二纺纶蜂窝层构成纺纶蜂窝结构板材。
3.根据权利要求2所述的防撞板,其特征在于,所述第一纺纶蜂窝层的厚度及所述第二纺纶蜂窝层的厚度均为5mm-10mm。
4.根据权利要求1所述的防撞板,其特征在于,所述缓冲层包括第一纺纶蜂窝层、第二纺纶蜂窝层及第三纺纶蜂窝层,所述第一纺纶蜂窝层、所述第二纺纶蜂窝层及所述第三纺纶蜂窝层的材料为纺纶蜂窝复合材料,所述第一纺纶蜂窝层、所述第二纺纶蜂窝层及所述第三纺纶蜂窝层通过功能树脂粘结,使所述第一纺纶蜂窝层、所述第二纺纶蜂窝层及所述第三纺纶蜂窝层构成纺纶蜂窝结构板材。
5.根据权利要求4所述的防撞板,其特征在于,所述第一纺纶蜂窝层的厚度、所述第二纺纶蜂窝层及所述第三纺纶蜂窝层的厚度均为5mm-10mm。
6.根据权利要求1所述的防撞板,其特征在于,包括撞击层;所述撞击层的材质为纺纶纤维,所述撞击层与所述缓冲层通过功能树脂粘结。
7.根据权利要求6所述的防撞板,其特征在于,包括吸能层;所述吸能层的材质为高分子聚合物,所述吸能层与所述缓冲层通过功能树脂粘结。
8.根据权利要求7所述的防撞板,其特征在于,所述高分子聚合物为聚氨酯发泡材料。
9.根据权利要求2-8任一项所述的防撞板,其特征在于,所述功能树脂为 双酚A型环氧树脂。
10.如权利要求1-9任一项所述的防撞板的制造方法,具体步骤包括:
步骤1、根据飞机的型号及飞机机头防撞部位的大小,确定所需防撞板的尺寸;
步骤2、根据步骤1确定的防撞板的尺寸,制作防撞板的热模压模具;
步骤3、根据步骤1确定的防撞板的尺寸,制作相应尺寸的撞击层、缓冲层及吸能层;
步骤4、将步骤3的撞击层、缓冲层依次放入步骤1的模具中,并在撞击层与缓冲层之间涂覆双酚A型环氧树脂;
步骤5、将步骤4所得模具放入热模压设备中,加压使撞击层及缓冲层的间隙小于0.1mm-0.2mm,继而保压,保压时间为5min-15min;
步骤6、脱模,并在压合后的缓冲层的表面贴覆吸能层,吸能层为高分子聚合物。
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