CN108099281A - 一种飞机机头用复合材料抗鸟撞挡板 - Google Patents

一种飞机机头用复合材料抗鸟撞挡板 Download PDF

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CN108099281A
CN108099281A CN201711446315.9A CN201711446315A CN108099281A CN 108099281 A CN108099281 A CN 108099281A CN 201711446315 A CN201711446315 A CN 201711446315A CN 108099281 A CN108099281 A CN 108099281A
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composite material
bird
composite
baffle
plane nose
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CN108099281B (zh
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陈以蔚
秦贞明
王荣惠
翟文
李峰
李树虎
贾华敏
王丹勇
魏化震
徐井利
魏汝斌
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Shandong Non Metallic Material Research Institute
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Shandong Non Metallic Material Research Institute
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Abstract

本发明的飞机机头用复合材料抗鸟撞挡板，由牙板和复合材料板构成，牙板位于复合材料板的外侧。牙板表面分布有突起，鸟撞上后会起到击碎其鸟骨及分散撞击力的作用；复合材料板的夹心板采用复合材料面板，与传统铝板相比，可以起到减重及提高其强度的作用；复合材料板的韧性复合材料层放置于刚性复合材料层上方，在受到撞击作用力时，上层起到吸能和防穿透作用，下层则能够将冲击力更大范围传递到下方，减低下方单位面积上的受力。本发明的飞机机头用复合材料抗鸟撞挡板，由于抗撞击能力强，其后方不需安装泡沫板，从而减小了体积，提高了雷达罩的可维修性。

Description

一种飞机机头用复合材料抗鸟撞挡板
技术领域
本发明属于复合材料领域，特别是一种飞机机头用复合材料抗鸟撞挡板。
背景技术
目前，在飞机雷达罩区域进行结构设计时，为了满足抗鸟撞要求，在机头雷达舱内增加了抗鸟撞蜂窝挡板组件，该组件是由铝合金板、铝蜂窝夹芯结构以及PMI泡沫板构成，其中，铝蜂窝夹芯结构位于两层铝合金板之间，PMI泡沫板位于最后方。
这种结构的抗鸟撞蜂窝挡板，能够满足抗鸟撞要求，但其缺点是会遮挡雷达罩拆卸的通路，且PMI泡沫板与机头腹板为粘接，无法拆卸，对雷达罩的维修性影响较大；而且，该种结构的抗鸟撞蜂窝挡板组件引起该区域增重较多，不利于提高飞机的经济性。
发明内容
本发明所要解决的技术问题是提供一种飞机机头用复合材料抗鸟撞挡板。
为实现上述目的，本发明采用的技术方案是：在抗鸟撞挡板的最外侧设置带有突起的牙板，牙板下方设置复合材料板，从而在提高抗撞击能力的同时，还能减小体积，减轻自身重量，实现了本发明的目的。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，包括铝板，其上面设置连接孔，其特征在于：还包括复合材料板；所述铝板为牙板，其表面设置有突起；复合材料板上设置有连接孔，位置与牙板的连接孔对应；牙板位于复合材料板上方，突起朝上。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述突起为棱锥结构或截面是倒V形的条状结构，底部中空，其顶部锥角为45°-135°。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述突起顶部锥角为60°、90°或120°。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述突起与复合材料板之间的空腔填充泡沫材料。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述复合材料板有多层，由夹芯板、单层复合材料板或两者构成，夹芯板由上下蒙皮和蜂窝夹芯或泡沫材料构成，蒙皮为复合材料面板。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，其特征在于：单层复合材料板和复合材料面板由刚性复合材料或韧性复合材料制成。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述复合材料板的韧性复合材料层和刚性复合材料层交替放置。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述复合材料板（2）的韧性复合材料层，位于刚性复合材料层上方。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述复合材料板（2）的韧性复合材料层与刚性复合材料层之间设置有垫块。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，其特征在于：所复合材料板的最底层为韧性复合材料层。
本发明涉及的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述刚性复合材料面板为碳纤维复合材料板；所述韧性复合材料面板为芳纶纤维复合材料板或聚乙烯纤维复合材料板；所述蜂窝材料为铝蜂窝或芳纶蜂窝。
本发明的飞机机头用复合材料抗鸟撞挡板，其外侧牙板表面分布有棱锥结构或截面是倒V形条状结构的突起，鸟撞上后会起到击碎其鸟骨及分散撞击力的作用，突起的侧面为倾斜结构，同样可以起到分散撞击力作用，突起的底部中空，可以起到吸能作用，在空腔中填充泡沫材料，可以提高其刚性，增强抗撞击能力；复合材料板的夹心板蒙皮采用复合材料面板，与传统的铝板相比，可以起到减重以及提高其强度的作用；复合材料板的韧性复合材料层放置于刚性复合材料层上方，在受到撞击作用力时，上层能承受较大变形，起到吸能和防穿透作用，下层则能够将冲击力更大范围传递到下方，减低下方单位面积上的受力；在两者之间留有小的空隙，可以将上述优点进一步扩大；复合材料板的韧性复合材料层和刚性复合材料层交替放置，由于材料的不同导致声阻抗的差异，可有效改变冲击波在不同介质间的反射和投射传播规律，起到衰减能量的作用；复合材料板的最底层设置韧性复合材料层，由于其后方留有较大空隙，需要时可以将其吸能和防穿透能力最大化。
本发明的飞机机头用复合材料抗鸟撞挡板，由于抗撞击能力强，其后方不需安装PMI泡沫板，从而大大减小了体积，提高了雷达罩的可维修性。
附图说明
图1给出的是第一个实施例中复合材料抗鸟撞挡板剖视图；
图2给出的是第一个实施例中牙板的结构示意图；
图3给出的是第三个实施例中牙板的结构示意图；
图4给出的是第四个实施例中复合材料抗鸟撞挡板的剖视图；
图5给出的是第五个实施例中复合材料板第二层的俯视图。
其中，1-牙板，2-复合材料板，3-突起，垫板4。
具体实施方式
下面结合附图和具体实施方式，对本发明作进一步详述，但不作为对技术方案的限制。
实施例一
飞机机头用复合材料抗鸟撞挡板，是由牙板1和复合材料板2构成，如图1所示。
牙板1，由厚1.5mm的 2024-T3铝合金板制成，表面分布连续排列的突起3，如图2所示。突起3为条状结构，截面呈倒V形，顶端为尖角结构，其顶部锥角为135°。牙板1上设置有连接孔，该孔的周围区域为平面结构。
复合材料板2由三层构成，第一、二层为夹芯板，由上下蒙皮和蜂窝夹芯粘接而成，第三层为芳纶纤维复合材料板。其中，第一层夹芯板的上下蒙皮都为芳纶纤维复合材料面板，由K-129芳纶纤维布和环氧树脂制成，密度1.3g/cm3，厚1mm；第二层夹芯板的上下蒙皮都为碳纤维复合材料面板，由3K平纹碳纤维布和环氧树脂制成，密度1.7g/cm3，厚1mm；蜂窝夹芯为铝蜂窝，型号AMS-C-7438-3/16-5052-0.002-5.7，厚12.7mm；第三层的芳纶纤维复合材料板，由K-129芳纶纤维布和环氧树脂制成，密度1.3g/cm3，厚2mm。复合材料板2上设置连接孔，位置与牙板1的连接孔对应。
牙板1位于复合材料板2的顶部，其突起3的尖角部位朝上。
借助螺栓通过连接孔，将复合材料抗鸟撞挡板固定在飞机机头雷达舱内。
实施例二
飞机机头用复合材料抗鸟撞挡板，是由牙板1和复合材料板2构成。
牙板1，由厚1.2mm的 2024-T3铝合金板制成，表面分布连续排列的突起3。突起3为条状结构，截面呈倒V形，顶端为倒圆角结构，其顶部锥角为120°。牙板1上设置有连接孔，该孔的周围区域为平面结构。
复合材料板2由四层构成，第一、三层为夹芯板，由上下蒙皮和蜂窝夹芯粘接而成，第二、四层为芳纶纤维复合材料板。两层夹芯板的上下蒙皮都为碳纤维复合材料面板，由单向碳纤维布和环氧树脂制成，密度1.7g/cm3，厚1mm；蜂窝夹芯结构为芳纶蜂窝，采用HEXEL公司生产的HRH-10航空级芳纶蜂窝，六角芯格，厚10mm；两层芳纶纤维复合材料板，由K-129芳纶纤维布和环氧树脂制成，密度1.3g/cm3，厚2mm。复合材料板2上设置连接孔，位置与牙板1的连接孔对应。
牙板1位于复合材料板2的顶部，其突起3的圆角部位朝上，突起3的中空底部填充聚氨酯泡沫。
借助螺栓通过连接孔，将复合材料抗鸟撞挡板固定在飞机机头雷达舱内。
实施例三
飞机机头用复合材料抗鸟撞挡板，是由牙板1和复合材料板2构成。
牙板1，由厚1mm的 2024-T3铝合金板制成，表面分布连续排列的突起3，如图3所示。突起3为棱锥结构，上尖下方，底边为正方形，边长44mm，相对锥面之间的夹角为90°，牙板1上设置有连接孔，该孔的周围区域为平面结构。
复合材料板2由三层构成，都为夹芯板，如图4所示，由上下蒙皮和蜂窝夹芯粘接而成。其中，第一层夹芯板的上下蒙皮为聚乙烯纤维复合材料面板，由聚乙烯纤维正交布和环氧树脂制成，密度1.0 g/cm3，厚1mm；第二、三层夹芯板的上下蒙皮都为碳纤维复合材料面板，由3K平纹碳纤维布和环氧树脂制成，密度1.7g/cm3，厚1mm；蜂窝夹芯结构为芳纶蜂窝，采用HEXEL公司生产的HRH-10航空级芳纶蜂窝，六角芯格，厚10mm。复合材料板2上设置连接孔，位置与牙板1的连接孔对应。
牙板1位于复合材料板2的顶部，其突起3的尖角部位朝上。
借助螺栓通过连接孔，将复合材料抗鸟撞挡板固定在飞机机头雷达舱内。
实施例四
飞机机头用复合材料抗鸟撞挡板，是由牙板1和复合材料板2构成。
牙板1，由厚1mm的 2024-T3铝合金板制成，表面分布连续排列的突起3。突起3为棱锥结构，上尖下方，底边为40mm×30 mm的长方形，相对锥面之间的夹角为60°，牙板1上设置有连接孔，该孔的周围区域为平面结构。
复合材料板2由三层构成，都为夹芯板，由上下蒙皮和蜂窝夹芯粘接而成。其中，三层夹芯板的上蒙皮为碳纤维复合材料面板，由3K平纹碳纤维布和环氧树脂制成，密度1.7g/cm3，厚1mm；下蒙皮为芳纶纤维复合材料面板，由K-129芳纶纤维布和环氧树脂制成，密度1.3g/cm3，厚1mm；蜂窝夹芯结构为PMI泡沫，密度0.19 g/cm3，厚15mm。复合材料板2上设置连接孔，位置与牙板1的连接孔对应。
牙板1位于复合材料板2的顶部，其突起3的尖角部位朝上。
借助螺栓通过连接孔，将复合材料抗鸟撞挡板固定在飞机机头雷达舱内。
实施例五
飞机机头用复合材料抗鸟撞挡板，是由牙板1和复合材料板2构成。
牙板1，由厚0.8mm 的2024-T3铝合金板制成，表面均匀排列突起3。突起3为棱锥结构，上尖下方，底边为半径40mm圆形，顶部锥角为45°。牙板1上设置有连接孔，该孔的周围区域为平面结构。
复合材料板2由三层构成，都为夹芯板，由上下蒙皮和蜂窝夹芯粘接而成。其中，第一、三层夹芯板的上下蒙皮都为芳纶纤维复合材料面板，由K-129芳纶纤维布和环氧树脂制成，密度1.3g/cm3，厚1mm；第二层夹芯板的上下蒙皮都为碳纤维复合材料面板，由3K平纹碳纤维布和酚醛树脂制成，密度1.7g/cm3，厚1mm；蜂窝夹芯结构为铝蜂窝，型号AMS-C-7438-3/16-5052-0.002-5.7，厚12.7mm。复合材料板2上设置连接孔，位置与牙板1的连接孔对应。在复合材料板2第二层的上蒙皮表面边缘处以及连接孔周围，分别粘接厚1mm、宽5mm的垫板4和厚1mm、边长20mm的垫板4，如图5所示，垫板4由碳纤维复合材料制成，其使得复合材料板2的第一、二层之间形成小的间隙。
牙板1位于复合材料板2的顶部，其突起3的尖角部位朝上，突起3的中空底部填充聚酰亚胺泡沫。
借助螺栓通过连接孔，将复合材料抗鸟撞挡板固定在飞机机头雷达舱内。

Claims (10)

1.一种飞机机头用复合材料抗鸟撞挡板，包括铝板，其上面设置连接孔，其特征在于：还包括复合材料板（2）；所述铝板为牙板（1），其表面设置有突起（3）；复合材料板（2）上设置有连接孔，位置与牙板（1）的连接孔对应；牙板（1）位于复合材料板（2）上方，突起（3）朝上。
2.根据权利要求1所述的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述突起（3）为棱锥结构或截面是倒V形的条状结构，底部中空，其顶部锥角为45°-135°。
3.根据权利要求2所述的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述突起（3）顶部锥角为60°、90°或120°。
4.根据权利要求2至3任一项所述的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述突起（3）与复合材料板（2）之间的空腔填充泡沫材料。
5.根据权利要求1所述的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述复合材料板（2）有多层，由夹芯板、单层复合材料板或两者构成，夹芯板由上下蒙皮和蜂窝夹芯或泡沫材料构成，蒙皮为复合材料面板。
6.根据权利要求5所述的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述单层复合材料板和复合材料面板由刚性复合材料或韧性复合材料制成。
7.根据权利要求6所述的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述复合材料板（2）的韧性复合材料层和刚性复合材料层交替放置。
8.根据权利要求6所述的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述复合材料板（2）的韧性复合材料层，位于刚性复合材料层上方。
9.根据权利要求8所述的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述复合材料板（2）的韧性复合材料层与刚性复合材料层之间设置有垫块（4）。
10.根据权利要求6至9任一项所述的飞机机头用复合材料抗鸟撞挡板，其特征在于：所述复合材料板（2）的最底层为韧性复合材料层。
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CN110571522A (zh) * 2019-03-21 2019-12-13 成都形水科技有限公司 宽频毫米波天线罩及其制备方法
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